Payload fairing separation analysis using constraint force equation

The dynamics associated with the jettisoning of the payload fairings from the parent launch vehicle is investigated. The separation dynamics of the fairings is derived using the constraint force equation (CFE) methodology. The analysis considers a spring and a hinge type separation system employed to jettison the fairings from the accelerating on-going stage. This study presents the results of determining the minimum permissible relative velocity of separation of the fairing and the spring force magnitude required for the separation velocity. The simulation results of the payload fairing separation dynamics are in good agreement with the results of the industry standard benchmark code. Furthermore, this result will be applied to design the parameter of the payload fairing separation system of Korea space launch vehicle (KSLV)-II.